Determine the normal force, the shear force, and the bending moment, 1) at the midpoint, 2) at the root of the oversimplified wing model of the following airliner. Assume that the engine create no thrust and there is no drag (i.e., consider only the forces and loading shown in the picture). Engine weight: WE= 28000 Newton (28 kN); Main landing gear reaction: N= 100000 Newton (100 kN) L = 15 m; L = 0.2xL; L = 0.15xL; 001 - 8710 N/m Distributed (continuous) load representing the lift created by the wing: 3 = 34000 Newton/meter (34 kN/m) Distributed (continuous) load representing the weight of the wing: Linearly decreasing from 01 (root) to = 001/2 0000 Represents the weight of the wing: Represents the lift wing created: 03 L 001 Normal force at the midpoint of the wing Shear force at the midpoint of the wing Bending moment at the midpoint of the wing Normal force at the root of the wing Shear force at the root of the wing Bending moment at the root of the wing WE .: Weight of the engine L Draw the following table to the page that you make the detailed calculations, and fill it with the results found. L2 VALUE 00 UNIT